CN107762661B - A kind of pulse-knocking injection ultra-combustion ramjet combined engine - Google Patents
A kind of pulse-knocking injection ultra-combustion ramjet combined engine Download PDFInfo
- Publication number
- CN107762661B CN107762661B CN201711200123.XA CN201711200123A CN107762661B CN 107762661 B CN107762661 B CN 107762661B CN 201711200123 A CN201711200123 A CN 201711200123A CN 107762661 B CN107762661 B CN 107762661B
- Authority
- CN
- China
- Prior art keywords
- pulse
- knocking
- injector
- injection
- combustion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/14—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines with external combustion, e.g. scram-jet engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/20—Composite ram-jet/pulse-jet engines
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
A kind of pulse-knocking injection ultra-combustion ramjet combined engine proposed by the present invention, is mainly made of components such as pulse detonation combustor, injectors.Injector includes injector inlet valve, mixing distance piece, secondary combustion chamber and injector jet pipe.Pulse-knocking injection super burn combined engine includes pulse-knocking injection and the big operation mode of ultra-combustion ramjet two.As flight Mach number Ma=0-5, with the work of pulse-knocking Ejector Mode.Under the ejector action for the pinking jet stream being discharged from detonating combustion device, more air enter air intake duct by injection, and air stagnation pressure increases.Pinking jet stream is blended with injection air, and fuel is sprayed into mixed airflow, carries out secondary pinking.At this point, the thrust of engine is mainly provided by pulse detonation combustor and injection second pulse knock system.In Ma > 5, engine switchs to ultra-combustion ramjet mode by pulse-knocking Ejector Mode, and aircraft continues to accelerate under the promotion of scramjet engine.
Description
Technical field
The present invention relates to technical field of engines, specially a kind of pulse-knocking injection ultra-combustion ramjet combined engine.
Background technique
Pulse-knocking engine (PDE) is that a kind of high-temperature high-pressure fuel gas generated using pulsed detonation wave generates thrust
From pressurization (about 13-15 times) power device, may operate within the scope of a very wide flight Mach number (Ma=0~5),
And subsonic speed, supersonic speed can efficient operation.In addition, detonating combustion mode has the thermal efficiency high (49%), burning speed
The remarkable advantage of rate fast (2000m/s).It is high using the PDE volumetric heat intensity of the technology, power device can be made to obtain bigger unit
Thrust and lower oil consumption rate.
Scramjet engine (Scramjet) can work in the even higher range of Ma=5-15, by flying height
Extend to atmosphere edge (50-60km).Although scramjet engine is suitable for hypersonic flight, but there is can not be quiet
Only start that (boosting is needed to accelerate), environmental pollution is serious, can only need dynamic with other forms the defects of endoatmosphere works
Force system work in combination.Rocket based combined cycle RBCC propulsion system needs to carry a large amount of fuel and oxidant, leads to its ratio
Rush small, flight cost height.Turbine base combination circulation TBCC propulsion system is faced with a great problem at present: general combustion gas whirlpool
(individual engine is precooled the maximum flight Mach number of turbine using integrated after-burner, incoming flow between 2-2.5
Etc. technologies maximum flight Mach number can be extended to 3 or so), be unable to reach the requirement (3.5-4) of relay Mach number.
Summary of the invention
In order to overcome, pulse-knocking engine High Mach number flying quality is insufficient and scramjet engine be unable to itself
The deficiency of starting, the present invention propose a kind of pulse-knocking injection ultra-combustion ramjet combined engine, the combined engine can 0 to
Work in 15 range of Mach numbers, realizes pulse-knocking mode and ultra-combustion ramjet mode conversion.
Air-breathing pulse detonation engine (APDE) efficient operation, pulse-knocking rocket can be sent out in the range of Ma=0-5
Motivation (PDRE) then can be in exoatmosphere efficient operation.Pulse-knocking mode and ultra-combustion ramjet mode are combined, utilized
Its performance complement forms pulse-knocking injection ultra-combustion ramjet combined engine, can overcome that RBCC specific impulse is small, at high cost and TBCC
Mach number switching problem realizes the steady operation in big fast domain and big airspace range (0-Ma15+, empty day are round-trip), reduces high Supersonic
The structure of fast propulsion system and the complexity of Model control mitigate weight, reduce volume, really realize that empty day combination promotes.
Fig. 1 give this assembly power it is basic composition and operation principle schematic diagram, mainly by pulse detonation combustor,
The components such as injector, injector inlet valve, mixing distance piece, secondary combustion chamber and jet pipe are constituted.According to flight condition difference
The operation mode of adjustable engine, by taking Single Stage To Orbit as an example, pulse-knocking ultra-combustion ramjet combined engine includes that pulse is quick-fried
Shake mode, ultra-combustion ramjet mode and pulse-knocking rocket mode.As flight Mach number Ma=0-5, using pulse-knocking injection
Modality work.Under the ejector action of the high-temperature fuel gas of detonation combustor discharge, more air are inhaled into injector, air
Stagnation pressure increases.High-temperature fuel gas is blended with injection air, and fuel is sprayed into mixed airflow, carries out second-time burning, generates two
Secondary pinking.At this point, the thrust of engine is mainly provided by pulse detonation combustor and injection second pulse knock system.In atmosphere
When in layer with flight Mach number Ma >=5 flight, engine is transformed into ultra-combustion ramjet mode, aircraft by pulse-knocking Ejector Mode
Continue to accelerate under the promotion of scramjet engine.Exoatmosphere, engine is with pulse-knocking rocket Modality work.
Therefore, using the scramjet engine of pulse-knocking technology there is ground to take off, autoacceleration, long voyage, height
The features such as specific impulse, has non-as the following hypersonic missile, re-entry space vehicle, the power for repeating the round-trip vehicle in the world
Often good application prospect.
Based on the above principles, the technical solution of the present invention is as follows:
A kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that: including pulse detonation combustor
(1), injector (5)；Pulse detonation combustor (1) is successively made of main detonation chamber (2) and pulse-knocking jet pipe (3)；Injector
It (5) successively include injector inlet valve (4), mixing distance piece (6), secondary combustion chamber (7) and injector jet pipe (9)；Injection
It also include nozzle (8) in device (5)；Pulse-knocking jet pipe (3) outlet of pulse detonation combustor (1) is passed through injector (5)
It mixes in distance piece (6)；Under pulse-knocking mode and ultra-combustion ramjet mode, only spray fuel, not spray are aoxidized in injector
Agent, by the air or supersonic airstream of injection as oxidant, under pulse-knocking rocket mode, in injector spray fuel and
Oxidant；Secondary combustion chamber (7) under pulse-knocking mode is as the combustion chamber under ultra-combustion ramjet mode.
Further preferred embodiment, a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that: main
Detonation chamber (2) shape is straight round tube, and the pulse-knocking jet pipe (3) being followed by is expanding nozzle；Injector jet pipe (9) is using expansion spray
Pipe.
Further preferred embodiment, a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that: arteries and veins
Burst shake burner has overlapping with injector, and pulse detonation combustor outlet and injector entrance section spacing are no more than 3
Main detonation chamber (2) internal diameter again.
Further preferred embodiment, a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that: spray
The spray mode of mouth (8) is opposite with direction of flow using tiltedly spray, injection direction；And fuel nozzle rear portion is fluted, for increasing
Air stream turbulence degree.
Further preferred embodiment, a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that:
In the mixing distance piece (6), the fuel and incoming flow that nozzle sprays are blended, and formation blending is equal before reaching secondary combustion chamber
Even turbulent flow；Under pulse-knocking mode, mixing distance piece (6) can be by the back-pressure of secondary combustion chamber (7) and pulse before
The isolation of detonating combustion device；Under ultra-combustion ramjet mode, mixing distance piece (6) can supersonic speed incoming flow to 5Ma or more slow down and increase
Pressure, and the back-pressure of secondary combustion chamber (7) is isolated.
Further preferred embodiment, a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that:
Under pulse-knocking mode, detonating combustion device work, the interior igniting of main detonation chamber (2) forms pinking, and passes through pulse-knocking jet pipe (3)
Into injector (5), injector inlet valve (4) is in the open state, and the injection air with certain speed enters injector
Inlet valve (4) then enters mixing distance piece (6), closes injector inlet valve (4), spray secondary fuel, secondary fuel
It is blended in mixing distance piece (6) atomization and with injection air；In the secondary combustion chamber (7), pinking jet stream light injection air with
The gaseous mixture of secondary fuel forms detonation wave propagation and goes out injector nozzle exit, and injector inlet valve is opened, outside air into
Enter injector, residual gas in injector is discharged.
Further preferred embodiment, a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that:
Under ultra-combustion ramjet mode, detonating combustion device does not work, and injector inlet valve (4) is in the open state always, supersonic airstream
Slow down pressurization in mixing distance piece (6), and after mix with the fuel of nozzle (8) spray, the burning in secondary combustion chamber (7) is fired
Gas after burning is discharged from injector jet pipe (9).
Further preferred embodiment, a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that:
Under pulse-knocking rocket mode, detonating combustion device work, the interior igniting of main detonation chamber (2) forms pinking, and sprays by pulse-knocking
It manages (3) and enters injector (5), injector inlet valve (4) is in close state, spray secondary fuel and oxidant, and mixed
Distance piece (6) atomization mixing is closed, in secondary combustion chamber (7), pinking jet stream lights the gaseous mixture of secondary fuel and oxidant, shape
Go out injector nozzle exit at detonation wave propagation, the gas after burning is discharged from injector jet pipe (9).
Beneficial effect
A kind of pulse-knocking injection ultra-combustion ramjet combined engine proposed by the present invention, beneficial effect is:
(1) it can work, can be voluntarily taken off under the conditions of subsonic speed and supersonic speed with ground, can also be emitted with carrier aircraft；
(2) steady operation in big fast domain and big airspace (Ma=0-15,0-50km) can be achieved；
(3) volume rate of combustion is high, can obtain bigger specific thrust and lower oil consumption；
(4) compared with turbine base combined cycle engine TBCC, complicated, expensive compressibility (compressor) is not needed,
Sub- combustion punching press mode is not needed to which the complexity and weight and volume etc. of entire propulsion system be greatly lowered yet.
(5) compared with rocket based combined cycle engine RBCC, pulse-knocking Ejector Mode is instead of rocket injection and Asia
Punching press mode is fired, and performance is higher.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1: the device of the invention figure；
Fig. 2: detonating combustion device expanding nozzle；
Fig. 3: injector expanding nozzle；
1. pulse detonation combustor in figure, 2. main detonation chambers, 3. detonating combustion device jet pipes, 4. injector inlet valves, 5.
Injector, 6. mixing distance pieces, 7. secondary combustion chambers, 8. fuel nozzles, 9. injector jet pipes.
Specific embodiment
The embodiment of the present invention is described below in detail, examples of the embodiments are shown in the accompanying drawings, wherein from beginning to end
Same or similar label indicates same or similar element or element with the same or similar functions.Below with reference to attached
The embodiment of figure description is exemplary, it is intended to is used to explain the present invention, and is not considered as limiting the invention.
In order to overcome, pulse-knocking engine High Mach number flying quality is insufficient and scramjet engine be unable to itself
The deficiency of starting, the present embodiment by using include pulse-knocking engine secondary combustion chamber and scramjet engine combustion
Burn room share etc. means, the advantages of pulse-knocking engine and scramjet engine, is combined, proposes a kind of pulse-knocking
Injection ultra-combustion ramjet combined engine, the combined engine can work in 0 to 15 range of Mach numbers, realize pulse-knocking mode
With ultra-combustion ramjet mode conversion and exoatmosphere, with pulse-knocking rocket Modality work.
Fig. 1 gives the basic composition and operation principle schematic diagram of this assembly power, mainly by pulse detonation combustor
1, injector 5 forms.According to the operation mode of the different adjustable engines of flight condition, by taking Single Stage To Orbit as an example, pulse is quick-fried
Shaking ultra-combustion ramjet combined engine includes pulse-knocking mode, ultra-combustion ramjet mode and pulse-knocking rocket mode.When flight horse
When conspicuous several Ma=0-5, using pulse-knocking Modality work.Under the ejector action of the high-temperature fuel gas of detonation combustor discharge, more
More air is inhaled into injector, and the stagnation pressure of air increases.High-temperature fuel gas is blended with injection air, is sprayed in mixed airflow
Enter fuel, carries out second-time burning, generate secondary pinking.At this point, the thrust of engine is mainly by pulse detonation combustor and injection
Second pulse knock system provides.When endoatmosphere is with flight Mach number Ma >=5 flight, engine is by pulse-knocking injection mould
State is transformed into ultra-combustion ramjet mode, and aircraft continues to accelerate under the promotion of scramjet engine.Exoatmosphere, engine with
Pulse-knocking rocket Modality work.
Specifically as shown in Figure 1, pulse detonation combustor 1 is successively made of main detonation chamber 2 and pulse-knocking jet pipe 3.Injection
Device 5 successively includes injector inlet valve 4, mixing distance piece 6, secondary combustion chamber 7 and injector jet pipe 9；It is also wrapped in injector 5
Contain nozzle 8.
2 shape of main detonation chamber of pulse detonation combustor 1 is straight round tube, and the pulse-knocking jet pipe 3 being followed by is expanding nozzle.
The outlet of pulse-knocking jet pipe 3 of pulse detonation combustor 1 is passed through in the mixing distance piece 6 of injector 5；Pulse detonation combustor with
Injector has in the main detonation chamber 2 of overlapping, pulse detonation combustor outlet and injector entrance section spacing no more than 3 times
Diameter.
The spray mode of nozzle 8 is opposite with direction of flow using tiltedly spray, injection direction；And fuel nozzle rear portion is fluted,
For increasing air stream turbulence degree, reinforce blending.Under pulse-knocking mode and ultra-combustion ramjet mode, only spray is fired in injector
Material, not spray oxidant, by the air or supersonic airstream of injection as oxidant, under pulse-knocking rocket mode, injection
Spray fuel and oxidant in device.
In the mixing distance piece (6), the fuel and incoming flow that nozzle sprays are blended, and before reaching secondary combustion chamber
It is formed and blends uniform turbulent flow；Under pulse-knocking mode, mixing distance piece (6) can by the back-pressure of secondary combustion chamber (7) with
Pulse detonation combustor isolation before；Under ultra-combustion ramjet mode, mixing distance piece (6) can be to the supersonic speed of 5Ma or more
Incoming flow, which is slowed down, to be pressurized, and the back-pressure of secondary combustion chamber (7) is isolated, wherein secondary combustion chamber (7) conduct under pulse-knocking mode
Combustion chamber under ultra-combustion ramjet mode.
Injector jet pipe (9) uses expanding nozzle.
When flight Mach number is less than 5, engine is under pulse-knocking mode, the work of detonating combustion device, main detonation chamber
(2) igniting forms pinking in, and enters injector (5) by pulse-knocking jet pipe (3), and injector inlet valve (4) is in and opens
State is opened, the injection air with certain speed enters injector inlet valve (4), then enters mixing distance piece (6), closes
Injector inlet valve (4), spray secondary fuel, secondary fuel are blended in mixing distance piece (6) atomization and with injection air；?
In secondary combustion chamber (7), pinking jet stream lights the gaseous mixture of injection air and secondary fuel, forms detonation wave propagation and goes out injector
Nozzle exit, injector inlet valve are opened, and outside air enters injector, residual gas in injector is discharged, is entered back into
Next circulation.
After flight Mach number is greater than 5, and at endoatmosphere, engine is under ultra-combustion ramjet mode, pinking combustion
Burner does not work, and injector inlet valve (4) is in the open state always, and supersonic airstream slows down in mixing distance piece (6) and increases
Pressure, and after mix with the fuel of nozzle (8) spray, burns in secondary combustion chamber (7), and the gas after burning is from injector jet pipe
(9) it is discharged.
At exoatmosphere, engine is under pulse-knocking rocket mode, the work of detonating combustion device, main detonation chamber (2)
Interior igniting forms pinking, and enters injector (5) by pulse-knocking jet pipe (3), and injector inlet valve (4), which is in, closes shape
State, spray secondary fuel and oxidant, and in mixing distance piece (6) atomization mixing, in secondary combustion chamber (7), pinking jet stream
It lights the gaseous mixture of secondary fuel and oxidant, forms detonation wave propagation and go out injector nozzle exit, the gas after burning is from drawing
Jet injection pipe (9) discharge.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (8)
1. a kind of pulse-knocking injection ultra-combustion ramjet combined engine, it is characterised in that: including pulse detonation combustor (1), draw
Emitter (5)；Pulse detonation combustor (1) is successively made of main detonation chamber (2) and pulse-knocking jet pipe (3)；Injector (5) is successively
Including injector inlet valve (4), mixing distance piece (6), secondary combustion chamber (7) and injector jet pipe (9)；In injector (5)
It also include nozzle (8)；Pulse-knocking jet pipe (3) outlet of pulse detonation combustor (1) is passed through the mixing isolation of injector (5)
In section (6)；Under pulse-knocking mode and ultra-combustion ramjet mode, only spray fuel in injector, not spray oxidant, by injection
Air or supersonic airstream as oxidant, under pulse-knocking rocket mode, spray fuel and oxidant in injector；Arteries and veins
The secondary combustion chamber (7) under shake mode is burst as the combustion chamber under ultra-combustion ramjet mode.
2. a kind of pulse-knocking injection ultra-combustion ramjet combined engine according to claim 1, it is characterised in that: main detonation chamber
(2) shape is straight round tube, and the pulse-knocking jet pipe (3) being followed by is expanding nozzle；Injector jet pipe (9) uses expanding nozzle.
3. a kind of pulse-knocking injection ultra-combustion ramjet combined engine according to claim 2, it is characterised in that: pulse-knocking
Burner has overlapping, the master of pulse detonation combustor outlet and injector entrance section spacing no more than 3 times with injector
Detonation chamber (2) internal diameter.
4. a kind of pulse-knocking injection ultra-combustion ramjet combined engine according to claim 1, it is characterised in that: nozzle (8)
Spray mode using tiltedly spray, injection direction is opposite with direction of flow；And nozzle rear portion is fluted, for increasing air stream turbulence
Degree.
5. a kind of pulse-knocking injection ultra-combustion ramjet combined engine according to claim 4, it is characterised in that: described mixed
It closes in distance piece (6), the fuel that nozzle sprays is blended with incoming flow, and the uniform rapids of blending is formed before reaching secondary combustion chamber
Stream；Under pulse-knocking mode, mixing distance piece (6) can fire the back-pressure of secondary combustion chamber (7) and pulse-knocking before
Burner isolation；Under ultra-combustion ramjet mode, mixing distance piece (6) can supersonic speed incoming flow to 5Ma or more slow down pressurization, and every
Back-pressure from secondary combustion chamber (7).
6. a kind of pulse-knocking injection ultra-combustion ramjet combined engine according to claim 5, it is characterised in that: quick-fried in pulse
It shakes under mode, the work of detonating combustion device, igniting forms pinking in main detonation chamber (2), and enters by pulse-knocking jet pipe (3) and draw
Emitter (5), injector inlet valve (4) is in the open state, and the injection air with certain speed enters injector inlet valve
Door (4) then enters mixing distance piece (6), closes injector inlet valve (4), spray secondary fuel, and secondary fuel is mixing
Distance piece (6) atomization is simultaneously blended with injection air；In secondary combustion chamber (7), pinking jet stream lights injection air and secondary combustion
The gaseous mixture of material forms detonation wave propagation and goes out injector nozzle exit, and injector inlet valve is opened, and outside air enters injection
Residual gas in injector is discharged device.
7. a kind of pulse-knocking injection ultra-combustion ramjet combined engine according to claim 5, it is characterised in that: rushed in super burn
Under pressing mold state, detonating combustion device does not work, and injector inlet valve (4) is in the open state always, and supersonic airstream is mixing
Distance piece (6) slows down pressurization, and after mix with the fuel of nozzle (8) spray, burns in secondary combustion chamber (7), after burning
Gas is discharged from injector jet pipe (9).
8. a kind of pulse-knocking injection ultra-combustion ramjet combined engine according to claim 5, it is characterised in that: quick-fried in pulse
Shake under rocket mode, the work of detonating combustion device, igniting forms pinking in main detonation chamber (2), and by pulse-knocking jet pipe (3) into
Enter injector (5), injector inlet valve (4) is in close state, spray secondary fuel and oxidant, and in mixing distance piece
(6) atomization mixing, in secondary combustion chamber (7), pinking jet stream lights the gaseous mixture of secondary fuel and oxidant, forms detonation wave
Injector nozzle exit is propagated out, the gas after burning is discharged from injector jet pipe (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711200123.XA CN107762661B (en) | 2017-11-27 | 2017-11-27 | A kind of pulse-knocking injection ultra-combustion ramjet combined engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711200123.XA CN107762661B (en) | 2017-11-27 | 2017-11-27 | A kind of pulse-knocking injection ultra-combustion ramjet combined engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107762661A CN107762661A (en) | 2018-03-06 |
| CN107762661B true CN107762661B (en) | 2019-05-10 |
Family
ID=61275404
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711200123.XA Active CN107762661B (en) | 2017-11-27 | 2017-11-27 | A kind of pulse-knocking injection ultra-combustion ramjet combined engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107762661B (en) |
Families Citing this family (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108708788B (en) * | 2018-05-29 | 2021-07-02 | 中国人民解放军国防科技大学 | Double-combustion-chamber ramjet engine and hypersonic aircraft |
| CN109139295B (en) * | 2018-10-22 | 2019-09-27 | 中国人民解放军国防科技大学 | Detonation stability control system and control method for scramjet engine |
| CN109441636B (en) * | 2018-12-21 | 2020-01-21 | 中国人民解放军空军工程大学 | Axial oil-supplementing cracking device |
| CN109931185B (en) * | 2019-03-20 | 2021-02-19 | 西北工业大学 | Integral detonation ramjet engine |
| CN110131071B (en) * | 2019-05-04 | 2021-06-15 | 西北工业大学 | Pulse detonation engine combustion chamber and detonation method thereof |
| CN111305972A (en) * | 2020-03-28 | 2020-06-19 | 西北工业大学 | Pulse detonation combustion chamber and air turbine rocket engine based on pulse detonation |
| CN112816218B (en) * | 2021-01-07 | 2022-07-15 | 中国人民解放军国防科技大学 | Rich fuel gas generation control system and control method |
| CN114320609B (en) * | 2022-03-03 | 2022-06-07 | 中国空气动力研究与发展中心计算空气动力研究所 | Fuel injection device of hypersonic-speed and scramjet engine |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2157909C1 (en) * | 1999-05-26 | 2000-10-20 | Центральный институт авиационного моторостроения им. П.И. Баранова | Supersonic pulse detonating ramjet engine and method of its functioning |
| US6857261B2 (en) * | 2003-01-07 | 2005-02-22 | Board Of Regents, The University Of Texas System | Multi-mode pulsed detonation propulsion system |
| CN101718236A (en) * | 2010-02-10 | 2010-06-02 | 周林 | Multitube pulse detonation combustion chamber communicated with jet deflector |
| CN102174913A (en) * | 2011-03-03 | 2011-09-07 | 西北工业大学 | Pulse detonation engine with ejector and method for processing main detonation tube |
| CN106640420A (en) * | 2016-12-30 | 2017-05-10 | 上海洲跃生物科技有限公司 | Pulse detonation engine with air entering from side portion |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100077726A1 (en) * | 2008-09-30 | 2010-04-01 | General Electric Company | Plenum air preheat for cold startup of liquid-fueled pulse detonation engines |
-
2017
- 2017-11-27 CN CN201711200123.XA patent/CN107762661B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| RU2157909C1 (en) * | 1999-05-26 | 2000-10-20 | Центральный институт авиационного моторостроения им. П.И. Баранова | Supersonic pulse detonating ramjet engine and method of its functioning |
| US6857261B2 (en) * | 2003-01-07 | 2005-02-22 | Board Of Regents, The University Of Texas System | Multi-mode pulsed detonation propulsion system |
| CN101718236A (en) * | 2010-02-10 | 2010-06-02 | 周林 | Multitube pulse detonation combustion chamber communicated with jet deflector |
| CN102174913A (en) * | 2011-03-03 | 2011-09-07 | 西北工业大学 | Pulse detonation engine with ejector and method for processing main detonation tube |
| CN106640420A (en) * | 2016-12-30 | 2017-05-10 | 上海洲跃生物科技有限公司 | Pulse detonation engine with air entering from side portion |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107762661A (en) | 2018-03-06 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107762661B (en) | A kind of pulse-knocking injection ultra-combustion ramjet combined engine | |
| US7669406B2 (en) | Compact, low pressure-drop shock-driven combustor and rocket booster, pulse detonation based supersonic propulsion system employing the same | |
| CN112902225B (en) | Multistage afterburning chamber with outer ring rotary detonation supercharged combustion chamber | |
| CN106050472A (en) | Turbo-rocket combined ramjet engine and operating method thereof | |
| US20140196460A1 (en) | Ramjet including a detonation chamber and aircraft comprising such a ramjet | |
| CN207093230U (en) | A kind of monoblock type rocket and ultra-combustion ramjet combined engine | |
| US11674437B2 (en) | Gas turbine power generation device | |
| WO2021243832A1 (en) | Pulse detonation combustion chamber having detonation gas energy distribution smooth structure | |
| CN109184953A (en) | A kind of rocket type rotation pinking punching press combined engine | |
| CN113137634A (en) | Variable-structure bimodal stamping combustion chamber | |
| CN108869095B (en) | Boundary suction control method with stable and self-sustaining supersonic detonation | |
| CN109899179B (en) | Scramjet engine capable of improving supersonic combustion performance of boron-containing rich-combustion solid propellant | |
| CN105604735A (en) | Hypersonic aircraft | |
| CN206397619U (en) | A kind of pulse-knocking engine of side exhaust | |
| CN111305972A (en) | Pulse detonation combustion chamber and air turbine rocket engine based on pulse detonation | |
| CN107218155B (en) | A kind of pulse ignite in advance can steady operation detonation engine | |
| CN204877714U (en) | Aviation, space flight, navigation in mixed engine of an organic whole | |
| CN107476898B (en) | A kind of air-breathing pulse detonation engine inhibits the structure of combustion gas forward pass | |
| CN216044045U (en) | Non-uniform compression system | |
| CN108757221A (en) | A kind of liquid Asia burning ramjet | |
| RU173530U1 (en) | Powerplant hypersonic aircraft | |
| CN1318748C (en) | Super combustion pressed engine | |
| RU163848U1 (en) | Pulsating Air-Jet Engine | |
| RU95108829A (en) | Combined ramjet engine | |
| CN104963788A (en) | Hybrid engine applicable for aviation, spaceflight and navigation |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |